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Unsteady Aerodynamic Modeling With Time-Varying Free-Stream Mach Numbers

dc.contributor.advisorLeishman, John Gen_US
dc.contributor.authorJose, Arun Isaacen_US
dc.date.accessioned2006-02-04T07:10:33Z
dc.date.available2006-02-04T07:10:33Z
dc.date.issued2005-12-02en_US
dc.identifier.urihttp://hdl.handle.net/1903/3143
dc.description.abstractThe development of a reduced-order unsteady airfoil theory is described for application to non-steady, subsonic compressible flows with variable free-stream Mach number. The airfoil theory, which is suitable for application to most types of comprehensive helicopter rotor analyses, is developed for arbitrary, time-dependent combined variations in angle of attack and Mach number. The approach is validated using CFD solutions based on the Euler equations. The new model is developed using the indicial theory as a basis, and shows excellent agreement with direct CFD solutions for a wide range of practical flows. For supercritical flows, nonlinearities associated with the formation and movement of shock waves are observed in the CFD solutions, which the unsteady airfoil theory proves inadequate. Overall, this study shows that the reduced-order unsteady aerodynamic theory provides significant improvements in sectional airloads predictions over existing methods that might be used in various types of comprehensive helicopter rotor analyses.en_US
dc.format.extent1627772 bytes
dc.format.mimetypeapplication/pdf
dc.language.isoen_US
dc.titleUnsteady Aerodynamic Modeling With Time-Varying Free-Stream Mach Numbersen_US
dc.typeThesisen_US
dc.contributor.publisherDigital Repository at the University of Marylanden_US
dc.contributor.publisherUniversity of Maryland (College Park, Md.)en_US
dc.contributor.departmentAerospace Engineeringen_US
dc.subject.pqcontrolledEngineering, Aerospaceen_US


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